Purpose: Manage output of sim parameters to file or stdout
Called by: FGSimExec
- ------------- Copyright (C) 1999 Jon S. Berndt (jsb@hal-pc.org) -------------
+ ------------- Copyright (C) 1999 Jon S. Berndt (jon@jsbsim.org) -------------
This program is free software; you can redistribute it and/or modify it under
the terms of the GNU Lesser General Public License as published by the Free Software
HISTORY
--------------------------------------------------------------------------------
12/02/98 JSB Created
+11/09/07 HDW Added FlightGear Socket Interface
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
INCLUDES
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
#include "FGOutput.h"
-#include "FGState.h"
#include "FGFDMExec.h"
#include "FGAtmosphere.h"
#include "FGFCS.h"
#include "FGAerodynamics.h"
#include "FGGroundReactions.h"
+#include "FGExternalReactions.h"
+#include "FGBuoyantForces.h"
#include "FGAircraft.h"
#include "FGMassBalance.h"
#include "FGPropagate.h"
#include "FGAuxiliary.h"
#include "FGInertial.h"
-
-#include <fstream>
+#include "FGPropulsion.h"
+#include "models/propulsion/FGEngine.h"
+#include "models/propulsion/FGTank.h"
+#include "models/propulsion/FGPiston.h"
+#include <sstream>
#include <iomanip>
+#include <cstring>
+#include <cstdlib>
+
+#include "input_output/net_fdm.hxx"
+#include "input_output/FGfdmSocket.h"
+
+#if defined(WIN32) && !defined(__CYGWIN__)
+# include <windows.h>
+#else
+# include <netinet/in.h> // htonl() ntohl()
+#endif
+
+static const int endianTest = 1;
+#define isLittleEndian (*((char *) &endianTest ) != 0)
+
+using namespace std;
namespace JSBSim {
-static const char *IdSrc = "$Id$";
+static const char *IdSrc = "$Id: FGOutput.cpp,v 1.48 2010/04/12 12:25:19 jberndt Exp $";
static const char *IdHdr = ID_OUTPUT;
+// (stolen from FGFS native_fdm.cxx)
+// The function htond is defined this way due to the way some
+// processors and OSes treat floating point values. Some will raise
+// an exception whenever a "bad" floating point value is loaded into a
+// floating point register. Solaris is notorious for this, but then
+// so is LynxOS on the PowerPC. By translating the data in place,
+// there is no need to load a FP register with the "corruped" floating
+// point value. By doing the BIG_ENDIAN test, I can optimize the
+// routine for big-endian processors so it can be as efficient as
+// possible
+static void htond (double &x)
+{
+ if ( isLittleEndian ) {
+ int *Double_Overlay;
+ int Holding_Buffer;
+
+ Double_Overlay = (int *) &x;
+ Holding_Buffer = Double_Overlay [0];
+
+ Double_Overlay [0] = htonl (Double_Overlay [1]);
+ Double_Overlay [1] = htonl (Holding_Buffer);
+ } else {
+ return;
+ }
+}
+
+// Float version
+static void htonf (float &x)
+{
+ if ( isLittleEndian ) {
+ int *Float_Overlay;
+ int Holding_Buffer;
+
+ Float_Overlay = (int *) &x;
+ Holding_Buffer = Float_Overlay [0];
+
+ Float_Overlay [0] = htonl (Holding_Buffer);
+ } else {
+ return;
+ }
+}
+
+
/*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
CLASS IMPLEMENTATION
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
Name = "FGOutput";
sFirstPass = dFirstPass = true;
socket = 0;
+ flightGearSocket = 0;
+ runID_postfix = 0;
Type = otNone;
SubSystems = 0;
enabled = true;
+ StartNewFile = false;
delimeter = ", ";
- Filename = "";
+ BaseFilename = Filename = "";
DirectivesFile = "";
+ output_file_name = "";
+
+ memset(&fgSockBuf, 0x00, sizeof(fgSockBuf));
Debug(0);
}
FGOutput::~FGOutput()
{
delete socket;
+ delete flightGearSocket;
OutputProperties.clear();
Debug(1);
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+bool FGOutput::InitModel(void)
+{
+ if (!FGModel::InitModel()) return false;
+
+ if (Filename.size() > 0 && StartNewFile) {
+ ostringstream buf;
+ string::size_type dot = BaseFilename.find_last_of('.');
+ if (dot != string::npos) {
+ buf << BaseFilename.substr(0, dot) << '_' << runID_postfix++ << BaseFilename.substr(dot);
+ } else {
+ buf << BaseFilename << '_' << runID_postfix++;
+ }
+ Filename = buf.str();
+ datafile.close();
+ StartNewFile = false;
+ dFirstPass = true;
+ }
+
+ return true;
+}
+
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
bool FGOutput::Run(void)
{
if (FGModel::Run()) return true;
- if (enabled && !State->IntegrationSuspended()&& !FDMExec->Holding()) {
+ if (enabled && !FDMExec->IntegrationSuspended()&& !FDMExec->Holding()) {
+ RunPreFunctions();
if (Type == otSocket) {
SocketOutput();
+ } else if (Type == otFlightGear) {
+ FlightGearSocketOutput();
} else if (Type == otCSV || Type == otTab) {
DelimitedOutput(Filename);
} else if (Type == otTerminal) {
} else {
// Not a valid type of output
}
+ RunPostFunctions();
}
return false;
}
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGOutput::SetType(string type)
+void FGOutput::SetType(const string& type)
{
if (type == "CSV") {
Type = otCSV;
delimeter = "\t";
} else if (type == "SOCKET") {
Type = otSocket;
+ } else if (type == "FLIGHTGEAR") {
+ Type = otFlightGear;
} else if (type == "TERMINAL") {
Type = otTerminal;
} else if (type != string("NONE")) {
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGOutput::DelimitedOutput(string fname)
+void FGOutput::DelimitedOutput(const string& fname)
{
streambuf* buffer;
string scratch = "";
if (fname == "COUT" || fname == "cout") {
buffer = cout.rdbuf();
} else {
- datafile.open(fname.c_str());
+ if (!datafile.is_open()) datafile.open(fname.c_str());
buffer = datafile.rdbuf();
}
ostream outstream(buffer);
+ outstream.precision(10);
+
if (dFirstPass) {
outstream << "Time";
if (SubSystems & ssSimulation) {
if (SubSystems & ssRates) {
outstream << delimeter;
outstream << "P (deg/s)" + delimeter + "Q (deg/s)" + delimeter + "R (deg/s)" + delimeter;
- outstream << "P dot (deg/s^2)" + delimeter + "Q dot (deg/s^2)" + delimeter + "R dot (deg/s^2)";
+ outstream << "P dot (deg/s^2)" + delimeter + "Q dot (deg/s^2)" + delimeter + "R dot (deg/s^2)" + delimeter;
+ outstream << "P_{inertial} (deg/s)" + delimeter + "Q_{inertial} (deg/s)" + delimeter + "R_{inertial} (deg/s)";
}
if (SubSystems & ssVelocities) {
outstream << delimeter;
outstream << "q bar (psf)" + delimeter;
+ outstream << "Reynolds Number" + delimeter;
outstream << "V_{Total} (ft/s)" + delimeter;
+ outstream << "V_{Inertial} (ft/s)" + delimeter;
outstream << "UBody" + delimeter + "VBody" + delimeter + "WBody" + delimeter;
outstream << "Aero V_{X Body} (ft/s)" + delimeter + "Aero V_{Y Body} (ft/s)" + delimeter + "Aero V_{Z Body} (ft/s)" + delimeter;
+ outstream << "V_{X_{inertial}} (ft/s)" + delimeter + "V_{Y_{inertial}} (ft/s)" + delimeter + "V_{Z_{inertial}} (ft/s)" + delimeter;
outstream << "V_{North} (ft/s)" + delimeter + "V_{East} (ft/s)" + delimeter + "V_{Down} (ft/s)";
}
if (SubSystems & ssForces) {
outstream << delimeter;
outstream << "F_{Drag} (lbs)" + delimeter + "F_{Side} (lbs)" + delimeter + "F_{Lift} (lbs)" + delimeter;
outstream << "L/D" + delimeter;
- outstream << "F_X (lbs)" + delimeter + "F_Y (lbs)" + delimeter + "F_Z (lbs)";
+ outstream << "F_{Aero x} (lbs)" + delimeter + "F_{Aero y} (lbs)" + delimeter + "F_{Aero z} (lbs)" + delimeter;
+ outstream << "F_{Prop x} (lbs)" + delimeter + "F_{Prop y} (lbs)" + delimeter + "F_{Prop z} (lbs)" + delimeter;
+ outstream << "F_{Gear x} (lbs)" + delimeter + "F_{Gear y} (lbs)" + delimeter + "F_{Gear z} (lbs)" + delimeter;
+ outstream << "F_{Ext x} (lbs)" + delimeter + "F_{Ext y} (lbs)" + delimeter + "F_{Ext z} (lbs)" + delimeter;
+ outstream << "F_{Buoyant x} (lbs)" + delimeter + "F_{Buoyant y} (lbs)" + delimeter + "F_{Buoyant z} (lbs)" + delimeter;
+ outstream << "F_{Total x} (lbs)" + delimeter + "F_{Total y} (lbs)" + delimeter + "F_{Total z} (lbs)";
}
if (SubSystems & ssMoments) {
outstream << delimeter;
- outstream << "L (ft-lbs)" + delimeter + "M (ft-lbs)" + delimeter + "N (ft-lbs)";
+ outstream << "L_{Aero} (ft-lbs)" + delimeter + "M_{Aero} ( ft-lbs)" + delimeter + "N_{Aero} (ft-lbs)" + delimeter;
+ outstream << "L_{Prop} (ft-lbs)" + delimeter + "M_{Prop} (ft-lbs)" + delimeter + "N_{Prop} (ft-lbs)" + delimeter;
+ outstream << "L_{Gear} (ft-lbs)" + delimeter + "M_{Gear} (ft-lbs)" + delimeter + "N_{Gear} (ft-lbs)" + delimeter;
+ outstream << "L_{ext} (ft-lbs)" + delimeter + "M_{ext} (ft-lbs)" + delimeter + "N_{ext} (ft-lbs)" + delimeter;
+ outstream << "L_{Buoyant} (ft-lbs)" + delimeter + "M_{Buoyant} (ft-lbs)" + delimeter + "N_{Buoyant} (ft-lbs)" + delimeter;
+ outstream << "L_{Total} (ft-lbs)" + delimeter + "M_{Total} (ft-lbs)" + delimeter + "N_{Total} (ft-lbs)";
}
if (SubSystems & ssAtmosphere) {
outstream << delimeter;
outstream << "Rho (slugs/ft^3)" + delimeter;
+ outstream << "Absolute Viscosity" + delimeter;
+ outstream << "Kinematic Viscosity" + delimeter;
+ outstream << "Temperature (R)" + delimeter;
outstream << "P_{SL} (psf)" + delimeter;
outstream << "P_{Ambient} (psf)" + delimeter;
+ outstream << "Turbulence Magnitude (ft/sec)" + delimeter;
+ outstream << "Turbulence X Direction (rad)" + delimeter + "Turbulence Y Direction (rad)" + delimeter + "Turbulence Z Direction (rad)" + delimeter;
outstream << "Wind V_{North} (ft/s)" + delimeter + "Wind V_{East} (ft/s)" + delimeter + "Wind V_{Down} (ft/s)";
}
if (SubSystems & ssMassProps) {
outstream << delimeter;
- outstream << "I_xx" + delimeter;
- outstream << "I_xy" + delimeter;
- outstream << "I_xz" + delimeter;
- outstream << "I_yx" + delimeter;
- outstream << "I_yy" + delimeter;
- outstream << "I_yz" + delimeter;
- outstream << "I_zx" + delimeter;
- outstream << "I_zy" + delimeter;
- outstream << "I_zz" + delimeter;
+ outstream << "I_{xx}" + delimeter;
+ outstream << "I_{xy}" + delimeter;
+ outstream << "I_{xz}" + delimeter;
+ outstream << "I_{yx}" + delimeter;
+ outstream << "I_{yy}" + delimeter;
+ outstream << "I_{yz}" + delimeter;
+ outstream << "I_{zx}" + delimeter;
+ outstream << "I_{zy}" + delimeter;
+ outstream << "I_{zz}" + delimeter;
outstream << "Mass" + delimeter;
- outstream << "X_cg" + delimeter + "Y_cg" + delimeter + "Z_cg";
+ outstream << "X_{cg}" + delimeter + "Y_{cg}" + delimeter + "Z_{cg}";
}
if (SubSystems & ssPropagate) {
outstream << delimeter;
- outstream << "Altitude (ft)" + delimeter;
+ outstream << "Altitude ASL (ft)" + delimeter;
+ outstream << "Altitude AGL (ft)" + delimeter;
outstream << "Phi (deg)" + delimeter + "Theta (deg)" + delimeter + "Psi (deg)" + delimeter;
outstream << "Alpha (deg)" + delimeter;
outstream << "Beta (deg)" + delimeter;
outstream << "Latitude (deg)" + delimeter;
outstream << "Longitude (deg)" + delimeter;
+ outstream << "X_{ECI} (ft)" + delimeter + "Y_{ECI} (ft)" + delimeter + "Z_{ECI} (ft)" + delimeter;
+ outstream << "X_{ECEF} (ft)" + delimeter + "Y_{ECEF} (ft)" + delimeter + "Z_{ECEF} (ft)" + delimeter;
+ outstream << "Earth Position Angle (deg)" + delimeter;
outstream << "Distance AGL (ft)" + delimeter;
- outstream << "Runway Radius (ft)";
+ outstream << "Terrain Elevation (ft)";
}
if (SubSystems & ssCoefficients) {
scratch = Aerodynamics->GetCoefficientStrings(delimeter);
}
if (OutputProperties.size() > 0) {
for (unsigned int i=0;i<OutputProperties.size();i++) {
- outstream << delimeter << OutputProperties[i]->GetName();
+ outstream << delimeter << OutputProperties[i]->GetPrintableName();
}
}
dFirstPass = false;
}
- outstream << State->Getsim_time();
+ outstream << FDMExec->GetSimTime();
if (SubSystems & ssSimulation) {
}
if (SubSystems & ssAerosurfaces) {
}
if (SubSystems & ssRates) {
outstream << delimeter;
- outstream << Propagate->GetPQR().Dump(delimeter) << delimeter;
- outstream << Propagate->GetPQRdot().Dump(delimeter);
+ outstream << (radtodeg*Propagate->GetPQR()).Dump(delimeter) << delimeter;
+ outstream << (radtodeg*Propagate->GetPQRdot()).Dump(delimeter) << delimeter;
+ outstream << (radtodeg*Propagate->GetPQRi()).Dump(delimeter);
}
if (SubSystems & ssVelocities) {
outstream << delimeter;
outstream << Auxiliary->Getqbar() << delimeter;
+ outstream << Auxiliary->GetReynoldsNumber() << delimeter;
outstream << setprecision(12) << Auxiliary->GetVt() << delimeter;
+ outstream << Propagate->GetInertialVelocityMagnitude() << delimeter;
outstream << setprecision(12) << Propagate->GetUVW().Dump(delimeter) << delimeter;
outstream << Auxiliary->GetAeroUVW().Dump(delimeter) << delimeter;
+ outstream << Propagate->GetInertialVelocity().Dump(delimeter) << delimeter;
outstream << Propagate->GetVel().Dump(delimeter);
+ outstream.precision(10);
}
if (SubSystems & ssForces) {
outstream << delimeter;
- outstream << Aerodynamics->GetvFs() << delimeter;
+ outstream << Aerodynamics->GetvFw().Dump(delimeter) << delimeter;
outstream << Aerodynamics->GetLoD() << delimeter;
+ outstream << Aerodynamics->GetForces().Dump(delimeter) << delimeter;
+ outstream << Propulsion->GetForces().Dump(delimeter) << delimeter;
+ outstream << GroundReactions->GetForces().Dump(delimeter) << delimeter;
+ outstream << ExternalReactions->GetForces().Dump(delimeter) << delimeter;
+ outstream << BuoyantForces->GetForces().Dump(delimeter) << delimeter;
outstream << Aircraft->GetForces().Dump(delimeter);
}
if (SubSystems & ssMoments) {
outstream << delimeter;
+ outstream << Aerodynamics->GetMoments().Dump(delimeter) << delimeter;
+ outstream << Propulsion->GetMoments().Dump(delimeter) << delimeter;
+ outstream << GroundReactions->GetMoments().Dump(delimeter) << delimeter;
+ outstream << ExternalReactions->GetMoments().Dump(delimeter) << delimeter;
+ outstream << BuoyantForces->GetMoments().Dump(delimeter) << delimeter;
outstream << Aircraft->GetMoments().Dump(delimeter);
}
if (SubSystems & ssAtmosphere) {
outstream << delimeter;
outstream << Atmosphere->GetDensity() << delimeter;
+ outstream << Atmosphere->GetAbsoluteViscosity() << delimeter;
+ outstream << Atmosphere->GetKinematicViscosity() << delimeter;
+ outstream << Atmosphere->GetTemperature() << delimeter;
outstream << Atmosphere->GetPressureSL() << delimeter;
outstream << Atmosphere->GetPressure() << delimeter;
- outstream << Atmosphere->GetWindNED().Dump(delimeter);
+ outstream << Atmosphere->GetTurbMagnitude() << delimeter;
+ outstream << Atmosphere->GetTurbDirection().Dump(delimeter) << delimeter;
+ outstream << Atmosphere->GetTotalWindNED().Dump(delimeter);
}
if (SubSystems & ssMassProps) {
outstream << delimeter;
- outstream << MassBalance->GetJ() << delimeter;
+ outstream << MassBalance->GetJ().Dump(delimeter) << delimeter;
outstream << MassBalance->GetMass() << delimeter;
- outstream << MassBalance->GetXYZcg();
+ outstream << MassBalance->GetXYZcg().Dump(delimeter);
}
if (SubSystems & ssPropagate) {
+ outstream.precision(14);
outstream << delimeter;
- outstream << Propagate->Geth() << delimeter;
- outstream << Propagate->GetEuler().Dump(delimeter) << delimeter;
+ outstream << Propagate->GetAltitudeASL() << delimeter;
+ outstream << Propagate->GetDistanceAGL() << delimeter;
+ outstream << (radtodeg*Propagate->GetEuler()).Dump(delimeter) << delimeter;
outstream << Auxiliary->Getalpha(inDegrees) << delimeter;
outstream << Auxiliary->Getbeta(inDegrees) << delimeter;
outstream << Propagate->GetLocation().GetLatitudeDeg() << delimeter;
outstream << Propagate->GetLocation().GetLongitudeDeg() << delimeter;
+ outstream.precision(18);
+ outstream << ((FGColumnVector3)Propagate->GetInertialPosition()).Dump(delimeter) << delimeter;
+ outstream << ((FGColumnVector3)Propagate->GetLocation()).Dump(delimeter) << delimeter;
+ outstream.precision(14);
+ outstream << Inertial->GetEarthPositionAngleDeg() << delimeter;
outstream << Propagate->GetDistanceAGL() << delimeter;
- outstream << Propagate->GetRunwayRadius();
+ outstream << Propagate->GetTerrainElevation();
+ outstream.precision(10);
}
if (SubSystems & ssCoefficients) {
scratch = Aerodynamics->GetCoefficientValues(delimeter);
outstream << Propulsion->GetPropulsionValues(delimeter);
}
+ outstream.precision(18);
for (unsigned int i=0;i<OutputProperties.size();i++) {
outstream << delimeter << OutputProperties[i]->getDoubleValue();
}
+ outstream.precision(10);
outstream << endl;
outstream.flush();
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+void FGOutput::SocketDataFill(FGNetFDM* net)
+{
+ unsigned int i;
+
+ // Version
+ net->version = FG_NET_FDM_VERSION;
+
+ // Positions
+ net->longitude = Propagate->GetLocation().GetLongitude(); // geodetic (radians)
+ net->latitude = Propagate->GetLocation().GetLatitude(); // geodetic (radians)
+ net->altitude = Propagate->GetAltitudeASL()*0.3048; // altitude, above sea level (meters)
+ net->agl = (float)(Propagate->GetDistanceAGL()*0.3048); // altitude, above ground level (meters)
+
+ net->phi = (float)(Propagate->GetEuler(ePhi)); // roll (radians)
+ net->theta = (float)(Propagate->GetEuler(eTht)); // pitch (radians)
+ net->psi = (float)(Propagate->GetEuler(ePsi)); // yaw or true heading (radians)
+
+ net->alpha = (float)(Auxiliary->Getalpha()); // angle of attack (radians)
+ net->beta = (float)(Auxiliary->Getbeta()); // side slip angle (radians)
+
+ // Velocities
+ net->phidot = (float)(Auxiliary->GetEulerRates(ePhi)); // roll rate (radians/sec)
+ net->thetadot = (float)(Auxiliary->GetEulerRates(eTht)); // pitch rate (radians/sec)
+ net->psidot = (float)(Auxiliary->GetEulerRates(ePsi)); // yaw rate (radians/sec)
+ net->vcas = (float)(Auxiliary->GetVcalibratedFPS()); // VCAS, ft/sec
+ net->climb_rate = (float)(Propagate->Gethdot()); // altitude rate, ft/sec
+ net->v_north = (float)(Propagate->GetVel(eNorth)); // north vel in NED frame, fps
+ net->v_east = (float)(Propagate->GetVel(eEast)); // east vel in NED frame, fps
+ net->v_down = (float)(Propagate->GetVel(eDown)); // down vel in NED frame, fps
+//---ADD METHOD TO CALCULATE THESE TERMS---
+ net->v_wind_body_north = (float)(Propagate->GetVel(eNorth)); // north vel in NED relative to airmass, fps
+ net->v_wind_body_east = (float)(Propagate->GetVel(eEast)); // east vel in NED relative to airmass, fps
+ net->v_wind_body_down = (float)(Propagate->GetVel(eDown)); // down vel in NED relative to airmass, fps
+
+ // Accelerations
+ net->A_X_pilot = (float)(Auxiliary->GetPilotAccel(1)); // X body accel, ft/s/s
+ net->A_Y_pilot = (float)(Auxiliary->GetPilotAccel(2)); // Y body accel, ft/s/s
+ net->A_Z_pilot = (float)(Auxiliary->GetPilotAccel(3)); // Z body accel, ft/s/s
+
+ // Stall
+ net->stall_warning = 0.0; // 0.0 - 1.0 indicating the amount of stall
+ net->slip_deg = (float)(Auxiliary->Getbeta(inDegrees)); // slip ball deflection, deg
+
+ // Engine status
+ net->num_engines = Propulsion->GetNumEngines(); // Number of valid engines
+
+ for (i=0; i<net->num_engines; i++) {
+ if (Propulsion->GetEngine(i)->GetRunning())
+ net->eng_state[i] = 2; // Engine state running
+ else if (Propulsion->GetEngine(i)->GetCranking())
+ net->eng_state[i] = 1; // Engine state cranking
+ else
+ net->eng_state[i] = 0; // Engine state off
+
+ switch (Propulsion->GetEngine(i)->GetType()) {
+ case (FGEngine::etRocket):
+ break;
+ case (FGEngine::etPiston):
+ net->rpm[i] = (float)(((FGPiston *)Propulsion->GetEngine(i))->getRPM());
+ net->fuel_flow[i] = (float)(((FGPiston *)Propulsion->GetEngine(i))->getFuelFlow_gph());
+ net->fuel_px[i] = 0; // Fuel pressure, psi (N/A in current model)
+ net->egt[i] = (float)(((FGPiston *)Propulsion->GetEngine(i))->GetEGT());
+ net->cht[i] = (float)(((FGPiston *)Propulsion->GetEngine(i))->getCylinderHeadTemp_degF());
+ net->mp_osi[i] = (float)(((FGPiston *)Propulsion->GetEngine(i))->getManifoldPressure_inHg());
+ net->oil_temp[i] = (float)(((FGPiston *)Propulsion->GetEngine(i))->getOilTemp_degF());
+ net->oil_px[i] = (float)(((FGPiston *)Propulsion->GetEngine(i))->getOilPressure_psi());
+ net->tit[i] = 0; // Turbine Inlet Temperature (N/A for piston)
+ break;
+ case (FGEngine::etTurbine):
+ break;
+ case (FGEngine::etTurboprop):
+ break;
+ case (FGEngine::etElectric):
+ break;
+ case (FGEngine::etUnknown):
+ break;
+ }
+ }
+
+
+ // Consumables
+ net->num_tanks = Propulsion->GetNumTanks(); // Max number of fuel tanks
+
+ for (i=0; i<net->num_tanks; i++) {
+ net->fuel_quantity[i] = (float)(((FGTank *)Propulsion->GetTank(i))->GetContents());
+ }
+
+
+ // Gear status
+ net->num_wheels = GroundReactions->GetNumGearUnits();
+
+ for (i=0; i<net->num_wheels; i++) {
+ net->wow[i] = GroundReactions->GetGearUnit(i)->GetWOW();
+ if (GroundReactions->GetGearUnit(i)->GetGearUnitDown())
+ net->gear_pos[i] = 1; //gear down, using FCS convention
+ else
+ net->gear_pos[i] = 0; //gear up, using FCS convention
+ net->gear_steer[i] = (float)(GroundReactions->GetGearUnit(i)->GetSteerNorm());
+ net->gear_compression[i] = (float)(GroundReactions->GetGearUnit(i)->GetCompLen());
+ }
+
+
+ // Environment
+ net->cur_time = (long int)1234567890; // Friday, Feb 13, 2009, 23:31:30 UTC (not processed by FGFS anyway)
+ net->warp = 0; // offset in seconds to unix time
+ net->visibility = 25000.0; // visibility in meters (for env. effects)
+
+
+ // Control surface positions (normalized values)
+ net->elevator = (float)(FCS->GetDePos(ofNorm)); // Norm Elevator Pos, --
+ net->elevator_trim_tab = (float)(FCS->GetPitchTrimCmd()); // Norm Elev Trim Tab Pos, --
+ net->left_flap = (float)(FCS->GetDfPos(ofNorm)); // Norm Flap Pos, --
+ net->right_flap = (float)(FCS->GetDfPos(ofNorm)); // Norm Flap Pos, --
+ net->left_aileron = (float)(FCS->GetDaLPos(ofNorm)); // Norm L Aileron Pos, --
+ net->right_aileron = (float)(FCS->GetDaRPos(ofNorm)); // Norm R Aileron Pos, --
+ net->rudder = (float)(FCS->GetDrPos(ofNorm)); // Norm Rudder Pos, --
+ net->nose_wheel = (float)(FCS->GetDrPos(ofNorm)); // *** FIX *** Using Rudder Pos for NWS, --
+ net->speedbrake = (float)(FCS->GetDsbPos(ofNorm)); // Norm Speedbrake Pos, --
+ net->spoilers = (float)(FCS->GetDspPos(ofNorm)); // Norm Spoiler Pos, --
+
+
+ // Convert the net buffer to network format
+ if ( isLittleEndian ) {
+ net->version = htonl(net->version);
+
+ htond(net->longitude);
+ htond(net->latitude);
+ htond(net->altitude);
+ htonf(net->agl);
+ htonf(net->phi);
+ htonf(net->theta);
+ htonf(net->psi);
+ htonf(net->alpha);
+ htonf(net->beta);
+
+ htonf(net->phidot);
+ htonf(net->thetadot);
+ htonf(net->psidot);
+ htonf(net->vcas);
+ htonf(net->climb_rate);
+ htonf(net->v_north);
+ htonf(net->v_east);
+ htonf(net->v_down);
+ htonf(net->v_wind_body_north);
+ htonf(net->v_wind_body_east);
+ htonf(net->v_wind_body_down);
+
+ htonf(net->A_X_pilot);
+ htonf(net->A_Y_pilot);
+ htonf(net->A_Z_pilot);
+
+ htonf(net->stall_warning);
+ htonf(net->slip_deg);
+
+ for (i=0; i<net->num_engines; ++i ) {
+ net->eng_state[i] = htonl(net->eng_state[i]);
+ htonf(net->rpm[i]);
+ htonf(net->fuel_flow[i]);
+ htonf(net->fuel_px[i]);
+ htonf(net->egt[i]);
+ htonf(net->cht[i]);
+ htonf(net->mp_osi[i]);
+ htonf(net->tit[i]);
+ htonf(net->oil_temp[i]);
+ htonf(net->oil_px[i]);
+ }
+ net->num_engines = htonl(net->num_engines);
+
+ for (i=0; i<net->num_tanks; ++i ) {
+ htonf(net->fuel_quantity[i]);
+ }
+ net->num_tanks = htonl(net->num_tanks);
+
+ for (i=0; i<net->num_wheels; ++i ) {
+ net->wow[i] = htonl(net->wow[i]);
+ htonf(net->gear_pos[i]);
+ htonf(net->gear_steer[i]);
+ htonf(net->gear_compression[i]);
+ }
+ net->num_wheels = htonl(net->num_wheels);
+
+ net->cur_time = htonl( net->cur_time );
+ net->warp = htonl( net->warp );
+ htonf(net->visibility);
+
+ htonf(net->elevator);
+ htonf(net->elevator_trim_tab);
+ htonf(net->left_flap);
+ htonf(net->right_flap);
+ htonf(net->left_aileron);
+ htonf(net->right_aileron);
+ htonf(net->rudder);
+ htonf(net->nose_wheel);
+ htonf(net->speedbrake);
+ htonf(net->spoilers);
+ }
+}
+
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
+void FGOutput::FlightGearSocketOutput(void)
+{
+ int length = sizeof(fgSockBuf);
+
+
+ if (flightGearSocket == NULL) return;
+ if (!flightGearSocket->GetConnectStatus()) return;
+
+ SocketDataFill(&fgSockBuf);
+ flightGearSocket->Send((char *)&fgSockBuf, length);
+}
+
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
void FGOutput::SocketOutput(void)
{
string asciiData, scratch;
socket->Append("Rho");
socket->Append("SL pressure");
socket->Append("Ambient pressure");
+ socket->Append("Turbulence Magnitude");
+ socket->Append("Turbulence Direction X");
+ socket->Append("Turbulence Direction Y");
+ socket->Append("Turbulence Direction Z");
socket->Append("NWind");
socket->Append("EWind");
socket->Append("DWind");
}
if (SubSystems & ssPropagate) {
socket->Append("Altitude");
- socket->Append("Phi");
- socket->Append("Tht");
- socket->Append("Psi");
- socket->Append("Alpha");
- socket->Append("Beta");
- socket->Append("Latitude (Deg)");
- socket->Append("Longitude (Deg)");
+ socket->Append("Phi (deg)");
+ socket->Append("Tht (deg)");
+ socket->Append("Psi (deg)");
+ socket->Append("Alpha (deg)");
+ socket->Append("Beta (deg)");
+ socket->Append("Latitude (deg)");
+ socket->Append("Longitude (deg)");
}
if (SubSystems & ssCoefficients) {
scratch = Aerodynamics->GetCoefficientStrings(",");
}
if (OutputProperties.size() > 0) {
for (unsigned int i=0;i<OutputProperties.size();i++) {
- socket->Append(OutputProperties[i]->GetName());
+ socket->Append(OutputProperties[i]->GetPrintableName());
}
}
}
socket->Clear();
- socket->Append(State->Getsim_time());
+ socket->Append(FDMExec->GetSimTime());
if (SubSystems & ssAerosurfaces) {
socket->Append(FCS->GetDaCmd());
socket->Append(FCS->GetDfPos());
}
if (SubSystems & ssRates) {
- socket->Append(Propagate->GetPQR(eP));
- socket->Append(Propagate->GetPQR(eQ));
- socket->Append(Propagate->GetPQR(eR));
- socket->Append(Propagate->GetPQRdot(eP));
- socket->Append(Propagate->GetPQRdot(eQ));
- socket->Append(Propagate->GetPQRdot(eR));
+ socket->Append(radtodeg*Propagate->GetPQR(eP));
+ socket->Append(radtodeg*Propagate->GetPQR(eQ));
+ socket->Append(radtodeg*Propagate->GetPQR(eR));
+ socket->Append(radtodeg*Propagate->GetPQRdot(eP));
+ socket->Append(radtodeg*Propagate->GetPQRdot(eQ));
+ socket->Append(radtodeg*Propagate->GetPQRdot(eR));
}
if (SubSystems & ssVelocities) {
socket->Append(Auxiliary->Getqbar());
socket->Append(Propagate->GetVel(eDown));
}
if (SubSystems & ssForces) {
- socket->Append(Aerodynamics->GetvFs()(eDrag));
- socket->Append(Aerodynamics->GetvFs()(eSide));
- socket->Append(Aerodynamics->GetvFs()(eLift));
+ socket->Append(Aerodynamics->GetvFw()(eDrag));
+ socket->Append(Aerodynamics->GetvFw()(eSide));
+ socket->Append(Aerodynamics->GetvFw()(eLift));
socket->Append(Aerodynamics->GetLoD());
socket->Append(Aircraft->GetForces(eX));
socket->Append(Aircraft->GetForces(eY));
socket->Append(Atmosphere->GetDensity());
socket->Append(Atmosphere->GetPressureSL());
socket->Append(Atmosphere->GetPressure());
- socket->Append(Atmosphere->GetWindNED().Dump(","));
+ socket->Append(Atmosphere->GetTurbMagnitude());
+ socket->Append(Atmosphere->GetTurbDirection().Dump(","));
+ socket->Append(Atmosphere->GetTotalWindNED().Dump(","));
}
if (SubSystems & ssMassProps) {
socket->Append(MassBalance->GetJ()(1,1));
socket->Append(MassBalance->GetXYZcg()(eZ));
}
if (SubSystems & ssPropagate) {
- socket->Append(Propagate->Geth());
- socket->Append(Propagate->GetEuler(ePhi));
- socket->Append(Propagate->GetEuler(eTht));
- socket->Append(Propagate->GetEuler(ePsi));
+ socket->Append(Propagate->GetAltitudeASL());
+ socket->Append(radtodeg*Propagate->GetEuler(ePhi));
+ socket->Append(radtodeg*Propagate->GetEuler(eTht));
+ socket->Append(radtodeg*Propagate->GetEuler(ePsi));
socket->Append(Auxiliary->Getalpha(inDegrees));
socket->Append(Auxiliary->Getbeta(inDegrees));
socket->Append(Propagate->GetLocation().GetLatitudeDeg());
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
-void FGOutput::SocketStatusOutput(string out_str)
+void FGOutput::SocketStatusOutput(const string& out_str)
{
string asciiData;
bool FGOutput::Load(Element* element)
{
string type="", parameter="";
- string name="", fname="";
+ string name="";
+ string protocol="tcp";
int OutRate = 0;
string property;
unsigned int port;
- FGXMLParse output_file_parser;
- Element *document, *property_element;
- ifstream* output_file = new ifstream();
+ Element *property_element;
string separator = "/";
-# ifdef macintosh
- separator = ";";
-# endif
if (!DirectivesFile.empty()) { // A directives filename from the command line overrides
- fname = DirectivesFile; // one found in the config file.
- } else {
- fname = element->GetAttributeValue("file");
- }
-
- if (!fname.empty()) {
- int len = fname.size();
- if (fname.find(".xml") != string::npos) {
- output_file_name = fname; // Use supplied name if last four letters are ".xml"
- } else {
- output_file_name = FDMExec->GetFullAircraftPath() + separator + fname + ".xml";
- }
- output_file->open(output_file_name.c_str());
- if (output_file->is_open()) {
- readXML(*output_file, output_file_parser);
- delete output_file;
- } else {
- delete output_file;
- cerr << "Could not open directives file: " << output_file_name << endl;
- return false;
- }
- document = output_file_parser.GetDocument();
+ output_file_name = DirectivesFile; // one found in the config file.
+ document = LoadXMLDocument(output_file_name);
+ } else if (!element->GetAttributeValue("file").empty()) {
+ output_file_name = FDMExec->GetRootDir() + element->GetAttributeValue("file");
+ document = LoadXMLDocument(output_file_name);
} else {
document = element;
}
- name = document->GetAttributeValue("name");
+ if (!document) return false;
+
+ name = FDMExec->GetRootDir() + document->GetAttributeValue("name");
type = document->GetAttributeValue("type");
SetType(type);
if (!document->GetAttributeValue("port").empty() && type == string("SOCKET")) {
port = atoi(document->GetAttributeValue("port").c_str());
socket = new FGfdmSocket(name, port);
+ } else if (!document->GetAttributeValue("port").empty() && type == string("FLIGHTGEAR")) {
+ port = atoi(document->GetAttributeValue("port").c_str());
+ if (!document->GetAttributeValue("protocol").empty())
+ protocol = document->GetAttributeValue("protocol");
+ if (protocol == "udp")
+ flightGearSocket = new FGfdmSocket(name, port, FGfdmSocket::ptUDP); // create udp socket
+ else
+ flightGearSocket = new FGfdmSocket(name, port, FGfdmSocket::ptTCP); // create tcp socket (default)
} else {
- Filename = name;
+ BaseFilename = Filename = name;
}
if (!document->GetAttributeValue("rate").empty()) {
OutRate = (int)document->GetAttributeValueAsNumber("rate");
SubSystems += ssPropulsion;
property_element = document->FindElement("property");
while (property_element) {
- string property = property_element->GetDataLine();
- OutputProperties.push_back(PropertyManager->GetNode(property));
+ string property_str = property_element->GetDataLine();
+ FGPropertyManager* node = PropertyManager->GetNode(property_str);
+ if (!node) {
+ cerr << fgred << highint << endl << " No property by the name "
+ << property_str << " has been defined. This property will " << endl
+ << " not be logged. You should check your configuration file."
+ << reset << endl;
+ } else {
+ OutputProperties.push_back(node);
+ }
property_element = document->FindNextElement("property");
}
- OutRate = OutRate>1000?1000:(OutRate<0?0:OutRate);
- rate = (int)(0.5 + 1.0/(State->Getdt()*OutRate));
+ SetRate(OutRate);
Debug(2);
return true;
}
+//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
+
+void FGOutput::SetRate(int rtHz)
+{
+ rtHz = rtHz>1000?1000:(rtHz<0?0:rtHz);
+ if (rtHz > 0) {
+ rate = (int)(0.5 + 1.0/(FDMExec->GetDeltaT()*rtHz));
+ Enable();
+ } else {
+ rate = 1;
+ Disable();
+ }
+}
+
//%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
// The bitmasked value choices are as follows:
// unset: In this case (the default) JSBSim would only print
}
switch (Type) {
case otCSV:
- cout << scratch << " in CSV format output at rate " << 1/(State->Getdt()*rate) << " Hz" << endl;
+ cout << scratch << " in CSV format output at rate " << 1/(FDMExec->GetDeltaT()*rate) << " Hz" << endl;
break;
case otNone:
+ default:
cout << " No log output" << endl;
break;
}
projects / flightgear.git / blobdiff